Airfoil shape for first stage compressor stator vane

ABSTRACT

A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

BACKGROUND OF THE INVENTION

The subject matter disclosed herein relates to compressor stator vanes,and more specifically, to a first stage compressor stator vane.

Compressors are used in a variety of industries and systems to compressa gas, such as air. For example, gas turbine engines typically include acompressor to provide compressed air for combustion and cooling.Compressors typically include a rotor assembly and a stator assembly. Inmulti-stage compressors, the rotor assembly may include multiple rows(e.g., rotor stages) each row having multiple rotor blades. Likewise,the stator assembly may include multiple rows (e.g., stator stages) eachrow having multiple stator vanes. The rotor assembly is designed torotate with respect to the stator assembly, compressing an intake fluidas the fluid traverses the compressor.

BRIEF DESCRIPTION OF THE INVENTION

Certain embodiments commensurate in scope with the originally claimedsubject matter are summarized below. These embodiments are not intendedto limit the scope of the claimed invention, but rather theseembodiments are intended only to provide a brief summary of possibleforms of the subject matter. Indeed, the invention may encompass avariety of forms that may be similar to or different from theembodiments set forth below.

In a first embodiment, a system includes an airfoil. The airfoilincludes a first suction portion of a nominal airfoil profilesubstantially in accordance with Cartesian coordinate values of X, Y,and Z of a suction side as set forth in TABLE I to a maximum of threedecimal places, wherein the X and Y values of the suction side arecoordinate values that couple together to define suction side sectionsof the first suction portion of the nominal airfoil profile at each Zcoordinate value, the suction side sections of the first suction portionof the nominal airfoil profile are coupled together to define the firstsuction portion, the airfoil includes an airfoil length along a Z axis,the first suction portion comprises a first portion length along the Zaxis, the first portion length is less than or equal to the airfoillength, and the Cartesian coordinate values of X, Y, and Z arenon-dimensional values convertible to dimensional distances.

In a second embodiment, a system includes an airfoil. The airfoilincludes a suction side of a nominal airfoil profile substantially inaccordance with Cartesian coordinate values of X, Y, and Z of thesuction side as set forth in TABLE I to a maximum of three decimalplaces, wherein the X and Y values of the suction side are coordinatevalues that couple together to define suction side sections of thesuction side of the nominal airfoil profile at each Z coordinate value,the suction side sections of the suction side of the nominal airfoilprofile are coupled together to define the suction side, and theCartesian coordinate values of X, Y, and Z are non-dimensional valuesconvertible to dimensional distances.

In a third embodiment, a system includes an airfoil. The airfoilincludes a nominal airfoil profile substantially in accordance withCartesian coordinate values of X, Y, and Z as set forth in TABLE I to amaximum of three decimal places, wherein the X and Y values arecoordinate values that couple together to define airfoil sections of thenominal airfoil profile at each Z coordinate value, the airfoil sectionsof the nominal airfoil profile are coupled together to define anentirety of the airfoil, and the Cartesian coordinate values of X, Y,and Z are non-dimensional values convertible to dimensional distances.

BRIEF DESCRIPTION OF THE DRAWINGS

These and other features, aspects, and advantages of the present subjectmatter will become better understood when the following detaileddescription is read with reference to the accompanying drawings in whichlike characters represent like parts throughout the drawings, wherein:

FIG. 1 is a block diagram of an embodiment of a gas turbine systemhaving a multi-stage axial compressor;

FIG. 2 is a cross-sectional side view of an embodiment of the gasturbine engine of FIG. 1, illustrating stages of blades and vanes of themulti-stage axial compressor;

FIG. 3 is side view of an embodiment of an airfoil of a compressor rotorblade or a compressor stator vane;

FIG. 4 is side view of an embodiment of an airfoil of a compressor rotorblade or a compressor stator vane;

FIG. 5 is a side view of an embodiment of an airfoil of the compressorrotor blade or a compressor stator vane; and

FIG. 6 is an axial view of an embodiment of the airfoil of thecompressor rotor blade or compressor stator vane of FIGS. 3-5.

DETAILED DESCRIPTION OF THE INVENTION

One or more specific embodiments of the present subject matter will bedescribed below. In an effort to provide a concise description of theseembodiments, all features of an actual implementation may not bedescribed in the specification. It should be appreciated that in thedevelopment of any such actual implementation, as in any engineering ordesign project, numerous implementation-specific decisions must be madeto achieve the developers' specific goals, such as compliance withsystem-related and business-related constraints, which may vary from oneimplementation to another. Moreover, it should be appreciated that sucha development effort might be complex and time consuming, but wouldnevertheless be a routine undertaking of design, fabrication, andmanufacture for those of ordinary skill having the benefit of thisdisclosure.

When introducing elements of various embodiments of the present subjectmatter, the articles “a,” “an,” “the,” and “said” are intended to meanthat there are one or more of the elements. The terms “comprising,”“including,” and “having” are intended to be inclusive and mean thatthere may be additional elements other than the listed elements.

The disclosed embodiments include a multi-stage axial compressor, whichmay be a standalone unit or part of a multi-stage rotary machine such asa gas turbine system. In certain embodiments, the multi-stage axialcompressor includes a plurality of rotor stages and corresponding statorstages, each rotor stage and stator stage including a plurality ofairfoils (e.g., blades or vanes) with a specific airfoil profile. Duringoperation, a compressible fluid (e.g., gas such as air, oxygen, oxygenenriched air, oxygen reduced air, exhaust gas, nitrogen, etc.) may enterthe multi-stage axial compressor through an inlet system, and each stageof the multi-stage axial compressor will generally increase the pressureand temperature of the compressible fluid by a certain amount. In a gasturbine system, a compressed fluid may then be delivered, for example,via an outlet system, to a combustor for combustion with a fuel. Theamount of pressure and temperature increase at each stage of themulti-stage axial compressor may depend on particular operatingconditions, such as speed, inlet boundary conditions (e.g., flow,pressure, temperature, composition, and so forth), outlet boundaryconditions (e.g., flow resistance, and so forth), and stage efficiency.

During compression, an energy level of the compressible fluid mayincrease as the compressible fluid flows through the multi-stage axialcompressor due to the exertion of a torque on the fluid by the rotatingrotor blades. The stator's stationary vanes slow the compressible fluid,converting a circumferential component of the flow into pressure. Anairfoil profile or design of the airfoil (e.g., rotor blades and/orstator vanes) may directly affect compression of the compressible fluid.Airfoil profiles described herein may be more optimized and matched forspecific velocities and turning speeds. Further, the airfoil profilesdescribed herein may be more optimized for specific stages of themulti-stage axial compressor with a specific total number of stages.Additionally, the airfoil profiles described herein may be designed forcompressor rotor blades, compressor stator vanes, or any combinationthereof. In certain embodiments, the airfoil profiles described hereinmay be designed for compressor rotor blades and/or compressor statorvanes in any one or more stages of a multi-stage axial compressor. Forexample, the airfoil profiles described herein may be designed forcompressor rotor blades and/or compressor stator vanes in stage 1, 2, 3,4, 5, 6, 7, 8, 9, 10, 11, 12, 13, and/or 14. As another example, theairfoil profiles described herein may be designed for a first stageairfoil, more specifically, a first stage stator vane, of an axialcompressor having between 12 and 14 stages. The airfoils (e.g., bladesor vanes) described herein may be described in terms of X, Y, and Zvalues set forth in certain table(s) described herein that defineairfoil sections of the airfoils. In certain embodiments the X, Y, and Zvalues may describe suction side airfoil surfaces, pressure side airfoilsurfaces, or a combination thereof. The X, Y, and Z values may includecoordinate values in a Cartesian coordinate system, including negativeand positive values denoting sides that are opposite to each other froma certain axis (e.g., X, Y, Z axis).

Turning now to FIG. 1, the figure is a block diagram of an embodiment ofa turbine system 10 that includes a gas turbine engine 12 and acontroller 14 (e.g., electronic and/or processor-based controller). Thecontroller 14 may be communicatively coupled to a variety of sensors 16and actuators 18 disposed in various components of the gas turbineengine 12. Signals received via the sensors 16 may be used to derivecontrol actions executable via the actuators 18. The illustrated gasturbine engine 12 includes a compressor 20 (e.g., a multi-stage axialcompressor or compressor section), a turbine 22 (e.g., a multi-stageturbine or turbine section), and fuel nozzles 24 coupled to one or morecombustors 26 (e.g., combustor section). The compressor 20 and turbine22 each may have any number of rows stages of rotor blades and statorvanes (e.g., 1 to 20). As discussed in detail below, an embodiment of anairfoil profile is provided for use with airfoils (e.g., rotor blades orstator vanes) in one or more stages of the compressor 20. However,before presenting details of the airfoil profile, the followingdiscussion provides a brief description of the gas turbine engine 12 andits operation.

In operation, the compressor 20 is configured to compress a compressiblefluid (e.g., gas such as air, oxygen, and/or exhaust gas), and deliverthe compressed fluid to the fuel nozzles 24 and/or combustors 26.Although the compressible fluid may include any suitable gas, thefollowing discussion may generally refer to the compressible fluid as anoxidant (e.g., air) as one non-limiting example. The fuel nozzles 24 areconfigured to supply fuel (e.g., from one or more fuel supplies) intothe one or more combustors 26 (e.g., in combustion chambers), whichcombust the fuel with the oxidant (e.g., air) to generate hot combustiongases to drive the turbine 22. The fuel nozzles 24 may be designed aspre-mix fuel nozzles 24 and/or diffusion fuel nozzles 24. Pre-mix fuelnozzles 24 mix the fuel with the oxidant (e.g., air) to create pre-mixtype flames. Diffusion fuel nozzles 24 do not premix the fuel with theoxidant, and thus create diffusion type flames. Regardless of the typeof flames, the hot combustion gas flows from the combustors 26 into theturbine 22, thereby driving rotation of one or more stages of turbineblades coupled to a turbine rotor and shaft 30 along an axis 32.Eventually, the hot combustion gas exits the turbine 22 through anexhaust outlet 28 (e.g., exhaust stack, exhaust end). In the illustratedembodiment, the shaft 30 is coupled to the compressor 20 and a load 36,such that rotation of the shaft 30 also drives rotation of thecompressor 20 and the load 36. The compressor 20 may intake the oxidant(e.g., air) through an air intake 34, which may include filters, thermalcontrol systems, or any other preconditioning systems. The load 36 mayinclude an electrical generator, a rotary machine, a propulsion systemof a vehicle, or any other suitable device.

The airfoil profile described in further detail below may be used in anystage of the compressor 20 (e.g., multi-stage axial compressor with anynumber of stages of rotor blades and stator vanes). The compressor 20may include rotating blades and stationary vanes (e.g., airfoils) thatmay be disposed in rows or stages, described in more detail below. Theoxidant (e.g., air) may be progressively compressed in stages or rows ofrotating blades and corresponding stator vanes as the air movesdownstream in the compressor 20. In the depicted embodiment, thecompressor 20 is a multi-stage axial compressor 20 having at least tworows or stages of blades and vanes. For example, in certain embodiments,the multi-stage axial compressor 20 may have 14 rows or stages ofcompressor blades and vanes.

It may be beneficial to illustrate a more detailed view of certaincomponents of the gas turbine engine 12. Accordingly, FIG. 2 is across-sectional side view of an embodiment of the compressor 20 of thegas turbine engine 12 of FIG. 1. Throughout the discussion of FIG. 2, aset of axes will be referenced. These axes are based on a cylindricalcoordinate system and point in an axial direction 38 (e.g., downstream),a radial direction 40, and a circumferential direction 42. For example,the axial direction 38 extends downstream through the compressor 20generally parallel to the axis 32, the radial direction 40 extends awayfrom the axis 32, and the circumferential direction 42 extends aroundthe axis 32.

In operation, air enters the compressor 20 in the axial direction 38through the air intake 34 and may be pressurized in the multi-stageaxial compressor 20. The compressed air may then be mixed with fuel forcombustion within the combustor 26 to drive the turbine 22 to rotate theshaft 30 in the circumferential direction 42 and, thus, the multi-stageaxial compressor 20 and the load 36. The rotation of the shaft 30 alsocauses one or more blades 44 (e.g., compressor rotor blades) within themulti-stage axial compressor 20 to draw in and pressurize the airreceived by the air intake 34.

The multi-stage axial compressor 20 may include a rotor assembly 46having multiple rotor blades 44 surrounded by a static casing 48 havingmultiple stator vanes 50 (e.g., variable stator vanes and/or fixedstator vanes). In some embodiments, the static casing 48 of thecompressor 20 or the air intake 34 may have one or more sets of inletguide vanes 52 (IGVs) (e.g., variable IGV stator vanes) that may controlflows into the compressor 20. Each variable stator vane 50 (includingeach variable IGV stator vane 52) may be configured to vary its vaneangle relative to the gas flow (e.g. air flow) by rotating the vane 50,52 about an axis of rotation (e.g., radially oriented vane shaft).However, each variable stator vane 50 may be otherwise stationaryrelative to the rotor blades 44. In certain embodiments, each variablestator vane 50 may be coupled to an actuator 18 (e.g., electric drive,pneumatic drive, or hydraulic drive), which is coupled to a controller14 configured to vary the vane angle in response to feedback fromsensors 16. Each fixed stator vane 50 may be configured to remain in afixed angular position, such that the vane angle does not vary. Thecompressor 20 may include a plurality of rows or stages 54, such asbetween 2 to 30, 2 to 25, 2 to 20, 2 to 14, or 2 to 10 rows or stages,or any specific number or range therebetween. In each stage, themulti-stage axial compressor 20 may include 2 to 1000, 5 to 500, or 10to 100 rotor blades 44, and 2 to 1000, 5 to 500, or 10 to 100 statorvanes 50. In particular, the illustrated embodiment of the multi-stageaxial compressor 20 includes 14 stages. It may be appreciated that eachstage 54 has a set of rotor blades 44 disposed at a first axial positionand a set of stator vanes 50 disposed at a second axial position alongthe length of the compressor 20. In other words, each stage 54 has therotor blades 44 and stator vanes 50 axially offset from one another,such that the compressor 20 has an alternating arrangement of rotorblades 44 and stator vanes 50 one set after another along the length ofthe compressor 20. Each set of rotor blades 44 extends (e.g., in aspaced arrangement) in the circumferential direction 42 about the shaft30, and each set of stator vanes 50 extends (e.g., in a spacedarrangement) in the circumferential direction 42 within the staticcasing 48. While the compressor 20 may include greater or fewer stages54 than 14, FIG. 2 illustrates an embodiment of the compressor 20 with14 stages 54 identified as follows: first stage 54 a, second stage 54 b,third stage 54 c, fourth stage 54 d, fifth stage 54 e, sixth stage 54 f,seventh stage 54 g, eighth stage 54 h, ninth stage 54 i, tenth stage 54j, eleventh stage 54 k, twelfth stage 54 l, thirteenth stage 54 m, andfourteenth stage 54 n. In certain embodiments, each stage 54 may includerotor blades 44 and stator vanes 50 (e.g., fixed stator vanes 50 and/orvariable stator vanes 50). For example, in certain embodiments, earlierstages 54 (e.g., 54 a, 54 b, 54 c, etc.) may include variable statorvanes 50, while later stages 54 may include fixed stator vanes 50.

The airfoil described in the TABLE I below may describe either a rotorblade 44 or a stator vane 50 of the compressor 20. For example, theairfoil described in the TABLE I below may be placed as a stator vane 50of the first stage 54 a. In use, the rotor blades 44 may rotatecircumferentially about the static casing 48 and the stator vanes 50.Rotation of the rotor blades 44 may result in air entering the airintake 34. The air is then subsequently compressed as it traverses thevarious stages 54 (e.g., first stage 54 a to fourteenth stage 54 n) ofthe compressor 20 and moves in the axial direction 38 downstream of themulti-stage axial compressor 20. The compressed air may then exitthrough an outlet 56 of the multi-stage axial compressor 20. The outlet56 may have a set of exit guide vanes 58 (EGVs). The compressed air thatexits the compressor 20 may be mixed with fuel, directed to thecombustor 26, directed to the turbine 22, or elsewhere in the turbinesystem 10.

Certain designs of the rotor blades 44 and stator vanes 50 (e.g.,airfoils) provide for a more efficient multi-stage axial compressor 20system. For example, certain rotor blade and/or stator vane (e.g.,airfoil) designs may improve compressor 20 efficiency and enableimproved operations for the turbine system 10. Referring now to FIG. 3,the figure is a side view of an embodiment of an airfoil 82 that may beincluded in the multi-stage axial compressor 20 as a rotor blade 44 orstator vane 50. In the particular embodiment, the airfoil 82 may beincluded in the first stage 54 a of the multi-stage axial compressor 20as a stator vane 50. In the depicted embodiment, the airfoil 82 isdisposed on a base 60, which may, in certain embodiments, be removablycoupled as a rotor blade 44 to the rotor assembly 46. That is, the base60 having the airfoil 82 may be removed from the rotor assembly 46, forexample, to inspect, repair, and/or replace the airfoil 82.Additionally, or in the alternative, the airfoil 82 may be removablycoupled as a stator vane 50 to the static casing 48. That is, the base60 having the airfoil 82 may be removed from the static casing 48, forexample, to inspect, repair, and/or replace the airfoil 82. The base 60may include a removable mount or coupling 59, such as a dovetail joint.For example, the coupling 59 may include a T-shaped structure, a hook,one or more lateral protrusions, one or more lateral slots, or anycombination thereof. The coupling 59 (e.g., dovetail joint) may beconfigured to mount into the rotor assembly 46 or the static casing 48in an axial direction 38, a radial direction 40, and/or acircumferential direction 42 (e.g., into an axial slot or opening, aradial slot or opening, and/or a circumferential slot or opening).

As further described herein, the airfoil 82 includes a suction side 62and a pressure side 64 disposed opposite from one another on the airfoil82 (i.e., opposite faces). The airfoil 82 also includes leading andtrailing edges 61 and 63 disposed opposite from one another on theairfoil 82 (e.g., opposite upstream and downstream edges). The suctionside 62, the pressure side 64, the leading edge 61, and the trailingedge 63 generally extend from the base 60 to a tip 68 of the airfoil 82.The leading and trailing edges, 61 and 63 respectively, may be describedas the dividing or intersecting lines between the suction side 62 andthe pressure side 64. In other words, the suction side 62 and thepressure sides 64 couple together with one another along the leadingedge 61 and the trailing edge 63, thereby defining an airfoil shapedcross-section that gradually changes lengthwise along the airfoil 82.The airfoil profile described in further detail below may be utilizedalong any portion or the entirety of the airfoil 82 between the base 60and the tip 68. For example, the portion having the disclosed airfoilprofile may include all or part of the suction side 62, all or part ofthe pressure side 64, or a combination thereof.

In operation, the rotor blades 44 rotate about an axis 66 exerting atorque on a working fluid, such as air, thus increasing energy levels ofthe fluid as the working fluid traverses the various stages 54 of themulti-stage axial compressor 20 on its way to the combustor 26. Thesuction side 62 creates and/or increases a suction force on the workingfluid, while the pressure side 64 creates and/or increases a pressurebias on the working fluid. The rotor blades 44 may be adjacent (e.g.,upstream and/or downstream) to the one or more stationary stator vanes50. The stator vanes 50 slow the working fluid during rotation of therotor blades 44, converting a circumferential component of movement ofthe working fluid flow into pressure. Accordingly, continuous rotationof the rotor blade 44 creates a continuous flow of compressed workingfluid, suitable for combustion via the combustor 26.

The airfoil 82 (e.g., rotor blade 44, stator vane 50) includes anairfoil length L measured from the tip 68 of the airfoil 82 to a bottomregion 70 of the airfoil 82 adjacent the base 60 (e.g., at anintersection of the airfoil 82 with the base 60). An X axis 72 liesparallel to the base 60 and to the rotational axis 66. The rotationalaxis 66 may be parallel to the axis 32 or the shaft 30. The X axis 72 isorthogonal to a Z axis 74 which bisects the airfoil 82. A Y axis 76(shown coming out of the plane of the drawing) is orthogonal to both theX axis 72 and the Z axis 74. The X axis 72 and the Y axis 76 may be usedto define an airfoil profile, shape, or section, for example, takenthrough line 6-6 at a point along the Z axis 74. That is, the airfoilprofile may include an outline of the surface (e.g., section) of theairfoil 82 (e.g., rotor blade 44, stator vane 50) at a point along the Zaxis 74. The airfoil profile may include X, Y, and Z values for thesuction side 62, and X, Y, and Z values for the pressure side 64. ACartesian coordinate system point 78 (e.g., origin) may be used todefine a zero point for the X axis 72, the Z axis 74, and the Y axis 76of the respective airfoil 82. TABLE I below lists variousnon-dimensionalized airfoil shapes for the suction side 62 and thecorresponding pressure side 64 disposed at locations along the Z axis 74from the bottom region 70 to the tip 68 of the airfoil 82.

The airfoil 82 may be described in terms of certain airfoil sectionscontaining various air foil shapes and corresponding rows of the TABLEI. For example, as illustrated in FIG. 4, the airfoil 82 may bedescribed via airfoil shapes disposed on one or more portions 80. Incertain embodiments, the portion 80 of the airfoil 82 may be describedas an area of interest, an area of greater importance, or a sweet spot,wherein the particular airfoil profile may have a greater impact on theperformance, efficiency, and other attributes of the airfoil 82 ascompared with other areas of the airfoil 82. However, the portion 80 mayinclude any area of the airfoil 82, regardless of importance. The one ormore portions 80 may include a suction side portion of the suction side62, a pressure side portion of the pressure side 64, or any combinationthereof. For example, the one or more portions 80 may include suctionside portions 62 and pressure side portions 64 that are offset from oneanother without any overlap along the Z axis 74, suction side portions62 and pressure side portions 64 that partially overlap along the Z axis74, or suction side portions 62 and pressure side portions 64 thatcompletely overlap along the Z axis 74. Portion 80 is shown as arectangle in dashed lines. More specifically, FIG. 4 is a side view ofan embodiment of the airfoil 82 illustrating the portion 80. Asdescribed above, the airfoil 82 may be the rotor blade 44 or the statorvane 50, such as the stator vane 50 of the first stage 54 a. Because thefigure depicts like elements to FIG. 3, the like elements areillustrated with like numbers. In the depicted embodiment, the airfoil82 includes the length L (e.g., total length), as mentioned previously,measured along the Z axis 74 (e.g., in the radial direction 40) from thetip 68 of the airfoil 82 to the bottom region 70 of the airfoil 82.

The portion 80 may begin at a distance or position d and include alength l extending away from the base 60 in the Z direction along the Zaxis 74. As appreciated, in embodiments having one or more suction sideportions 80 on the suction side 62 and/or one or more pressure sideportions 80 on the pressure side 64, each portion 80 may be defined by alength l and a position d. A zero value of the position d corresponds tothe bottom region 70 of the airfoil 82 adjacent the base 60 (e.g., at anintersection of the airfoil 82 with the base 60), which also correspondsto the coordinate origin 78. When d is zero and l is equal to L, theportion 80 includes the entirety of the airfoil 82 from the bottomregion 70 to the tip 68 of the airfoil 82. By varying values for d andl, portions 80 having varying lengths and start locations from thecoordinate origin 78 may be provided for defining the area of interest(e.g., sweet spot) along the airfoil 82. Each portion 80 may include oneor more adjacent airfoil shapes (e.g., airfoil sections or airfoilshapes 110) “stacked” on top of each other along the Z axis 74,described in more detail below with respect to FIG. 6 and TABLE I below.Each airfoil section or airfoil shape 110 corresponds to Cartesiancoordinate values of X, Y, and Z for a common Cartesian coordinate valueof Z in TABLE I. Furthermore, adjacent airfoil sections or airfoilshapes 110 correspond to the Cartesian coordinate values of X, Y, and Zfor adjacent Cartesian coordinate values of Z in the TABLE I.

With reference to TABLE I, the position d may be used to define a startposition (e.g., first Cartesian coordinate value of Z) of the portion 80in the Z direction along the Z axis 74, while a sum of the position dand the length l may be used to define an end position (e.g., lastCartesian coordinate value of Z) of the portion 80 in the Z directionalong the Z axis 74. In certain embodiments, the position d (e.g., startposition) may be selected directly from one of the Cartesian coordinatevalues of Z in TABLE I, and the sum of the position d and the length l(e.g., end position) may be selected directly from one of the Cartesiancoordinate values of Z in TABLE I. In other embodiments, the desiredvalues of the position d and the length l may be initially selectedwithout referencing TABLE I, and then TABLE I may be subsequentlyanalyzed to select best fits of the Cartesian coordinate values of Z inTABLE I based on the desired values of d and l. For example, withreference to TABLE I, the start position of the portion 80 maycorrespond to the Cartesian coordinate value of Z equal to or nearest tothe value of the position d (e.g., start Z value). If the position d ismidway between adjacent Cartesian coordinate values of Z in TABLE I,then the lesser or greater Cartesian coordinate value of Z may beselected for the start position of the portion 80 (e.g., start Z value).Alternatively, in some embodiments, if a specific value of the positiond is desired but does not match the specific Cartesian coordinate valuesof Z in TABLE I, then regression analysis and/or curve fitting may beused to analyze the data in TABLE I and interpolate new Cartesiancoordinate values of X, Y, Z to enable use of the desired d value.Similarly, with reference to TABLE I, the end position (e.g., end Zvalue) may correspond to the Cartesian coordinate value of Z equal to ornearest to the sum of the position d and the length l. If the sum of theposition d and the length l is midway between adjacent Cartesiancoordinate values of Z in TABLE I, then the lesser or greater Cartesiancoordinate value of Z may be selected for the end position (e.g., end Zvalue). Alternatively, in some embodiments, if a specific value of thelength l is desired but the sum of the position d and the length l doesnot match the specific Cartesian coordinate values of Z in TABLE I, thenregression analysis and/or curve fitting may be used to analyze the datain TABLE I and interpolate new Cartesian coordinate values of X, Y, Z toenable use of the desired l value.

In certain embodiments, the portion 80 may be defined by the Cartesiancoordinate values of X, Y, and Z corresponding to the start Z value, theend Z value, and all intermediate Z values in TABLE I. However, in someembodiments, if the Z values do not match the desired start and endpositions, then the portion 80 may be defined by the Cartesiancoordinate values of X, Y, and Z in TABLE I in the Z direction betweenthe start and end positions (e.g., based on the position d and lengthl). Furthermore, as discussed herein, the portion 80 may include theCartesian coordinate values of X, Y, and Z for the suction side 62(e.g., suction side profile 112—see FIG. 6), the pressure side 64 (e.g.,pressure side profile—see FIG. 6), or a combination thereof.

In certain embodiments, the portion 80 may include the airfoil profileof TABLE I only for the suction side 62 according to the position d andlength l, only for the pressure side 64 according to the position d andlength l, or for both the suction and pressure sides 62 and 64 accordingto the position d and length l. The position d of the portion 80 may begreater than or equal to approximately 0, 5, 10, 15, 20, 25, 30, 35, 40,45, 50, 55, 60, 65, 70, or 75 percent of the length L of the airfoil 82.Furthermore, the length l of the portion 80 may be greater than or equalto approximately 5, 10, 15, 20, 25, 30, 35, 40, 45, 50, 55, 60, 65, 70,75, 80, 85, 90, 95, or 100 percent of the length L of the airfoil 82.For example, the portion 80 selected from TABLE I may be the suctionside 62 of the outer third of the airfoil 82. In another example, theportion 80 selected from TABLE I may be both the suction side 62 and thepressure side 64 of an interior portion 80 of the airfoil 82, where d isgreater than 0 and l is less than L (e.g., l=0.3L).

Additionally or alternatively, a portion of the airfoil 82, such asportion 80, may be described in terms of a start height (e.g., firstposition) and a stop height (e.g., second position) along the Z axis 74(e.g., in the radial direction 40) as illustrated in FIG. 5.Collectively, the start and stop heights (e.g., first and secondpositions) define a range along the Z axis 74. Again, the portion (e.g.,80) of the airfoil 82 may be described as an area of interest, an areaof greater importance, or a sweet spot, wherein the particular airfoilprofile may have a greater impact on the performance, efficiency, andother attributes of the airfoil 82 as compared with other areas of theairfoil 82. However, the portion (e.g., 80) may include any area of theairfoil 82, regardless of importance. For example, as shown in FIG. 5,an embodiment of the airfoil 82 is illustrated with multiple definedheights 90, 92, 94, 96, 98, and 100 along the Z axis 74. The heights 90,92, 94, 96, 98, and 100 may divide the airfoil 82 into a plurality ofportions along the Z axis 74, wherein the plurality of portions may haveequal lengths along the Z axis 74 (e.g., five portions each being 20percent of the total length L of the airfoil 82). However, in someembodiments, the plurality of portions defined by the heights 90, 92,94, 96, 98, and 100 may have different lengths along the Z axis 74.Although the illustrated embodiment includes 6 heights (e.g., 90, 92,94, 96, 98, and 100) defining 5 portions, certain embodiments mayinclude any number of heights (e.g., 2 to 100 or more) defining anynumber of portions (e.g., 2 to 100 or more) with equal or differentlengths along the Z axis 74.

For example, certain embodiments may include 11 heights to define 10portions with equal or different lengths along the Z axis 74 (e.g., 10portions each being 10 percent of the total length L of the airfoil 82).By further example, certain embodiments may include 101 heights todefine 100 portions with equal or different lengths along the Z axis 74(e.g., 100 portions each being 1 percent of the total length L of theairfoil 82). In this manner, the heights may be used to define aspecific portion (e.g., 80) of the airfoil 82, wherein the specificportion (e.g., area of interest) may track the airfoil profile describedbelow in TABLE I. Again, similar to the discussion of FIG. 4, thespecific portion (e.g., 80) defined by the heights in FIG. 5 may trackthe airfoil profile of TABLE I along only the suction side 62, only thepressure side 64, or both the suction and pressure sides 62 and 64.Because FIG. 5 depicts like elements to FIG. 4, the like elements areillustrated with like numbers.

In the illustrated embodiment, the portion (e.g., 80) may be defined bythe start height and the stop height, wherein the start height is closerto the bottom region 70 than the stop height, and each of the start andstop heights may be selected from one of the heights 90, 92, 94, 96, 98,or 100. Multiple start and stop heights 90, 92, 94, 96, 98, 100 may bedefined to divide the airfoil 82 and define the portion (e.g., 80). Forexample, a first start height 92 and a first stop height 90 may describea first section or segment 102 (e.g., portion 80) of the airfoil 82, asecond start height 96 and a second stop height 92 may describe a secondsection or segment 104 (e.g., portion 80) of the airfoil 82, and a thirdstart height 96 and a third stop height 94 may describe a third sectionor segment 106 (e.g., portion 80) of the airfoil 82. As shown in FIG. 5,each height 90, 92, 94, 96, 98, 100 may define a start height for asegment, a stop height for the segment, or a start height for onesegment and a stop height for another segment. Each of the heights 90,92, 94, 96, 98, 100 may be selected to correspond to a differentCartesian coordinate value of Z in TABLE I. In certain embodiments, eachof the heights 90, 92, 94, 96, 98, 100 may be selected directly from oneof the Cartesian coordinate values of Z in TABLE I. In otherembodiments, the desired values of the heights 90, 92, 94, 96, 98, 100may be initially selected without referencing TABLE I, and then TABLE Imay be subsequently analyzed to select best fits of the Cartesiancoordinate values of Z in TABLE I based on the desired values of theheights 90, 92, 94, 96, 98, 100. For example, each of the heights 90,92, 94, 96, 98, 100 may correspond to the Cartesian coordinate value ofZ equal to or nearest to the value of the particular height 90, 92, 94,96, 98, or 100. If the height 90, 92, 94, 96, 98, or 100 is midwaybetween adjacent Cartesian coordinate values of Z in TABLE I, then thelesser or greater Cartesian coordinate value of Z may be selected forthe particular height 90, 92, 94, 96, 98, or 100. Alternatively, in someembodiments, if specific heights are desired but do not match thespecific Cartesian coordinate values of Z in TABLE I, then regressionanalysis and/or curve fitting may be used to analyze the data in TABLE Iand interpolate new Cartesian coordinate values of X, Y, Z to enable useof the desired heights. In some embodiments, if the Z values do notmatch the desired heights, then the portion 80 may be defined by theCartesian coordinate values of X, Y, and Z in TABLE I in the Z directionbetween the start and stop heights. Furthermore, with reference to TABLEI, the overall height dimension of each segment (e.g., 102, 104, 106)may be equal to an absolute value of the difference between the startand stop heights (e.g., Cartesian coordinate values of Z) for theparticular segment. In certain embodiments, an offset or correctionvalue may be used to account for negative values in TABLE I. Forexample, certain components of the airfoil 82, such as the bottom region70, may be disposed below the origin point 78 by a distance 108, andthus certain Z values may be negative denoting sections of airfoil 82below the origin point 78. Accordingly, the offset may be equal to anabsolute value of the smallest negative value given in TABLE I.

As mentioned earlier with respect to the portion 80 of FIG. 4, thesections 102, 104, and 106 (e.g., portion 80) of FIG. 5 may include oneor more airfoil shapes, profiles, or sections, such as an airfoil shapeshown in FIG. 6. More specifically, FIG. 6 is a cross-sectional top viewdepicting an embodiment of an airfoil shape 110 taken through line 6-6of FIGS. 3, 4, and 5, wherein the airfoil shape 110 may be included, forexample, in the portion 80 of the airfoil 82 (e.g., rotor blade 44,stator vane 50). As mentioned earlier, the airfoil 82 may be describedin terms of one or more airfoil shapes (e.g., sections) “stacked” on topof each other along the Z axis 74, such as the depicted airfoil shape110. To define the airfoil shape 110, a unique set or loci of points inspace are provided in TABLE I.

A Cartesian coordinate system of X, Y, and Z values given in TABLE Ibelow defines a suction side profile 112 and a pressure side profile 114of the airfoil shape 110 at various locations along the airfoil 82. Forexample, point 116 defines a first pair of suction side X and Y valuesat the Z value of line 6-6 of FIGS. 3-5, while point 118 defines asecond pair of pressure side X and Y values at the same Z value of FIGS.3-5. The X, Y, and Z values of TABLE I are set forth innon-dimensionalized units, and thus a variety of units of dimensions maybe used when the values are appropriately scaled by a scale factor F.The scale factor F may be substantially equal to 1, greater than 1, orless than 1. For example, the Cartesian coordinate values of X, Y, and Zmay be convertible to dimensional distances by multiplying the X, Y, andZ values by a constant number (e.g., 100). The number, used to convertthe non-dimensional values to dimensional distances, may be a fraction(e.g., ½, ¼, etc.), decimal fraction (e.g., 0.5, 1.5, 10.25, etc.),integer (e.g., 1, 2, 10, 100, etc.) or a mixed number (e.g., 1½, 10¼,etc.). The dimensional distances may be any suitable format (e.g.,inches, feet, millimeters, centimeters, etc.) These values exclude acoated region or coatings 120 of the airfoil 82. In other words, thesevalues correspond to the bare surface of the airfoil 82. The coatedregion 120 may include one or more coating layers, surface treatments,or a combination thereof, over the bare surface of the airfoil 82. TheCartesian coordinate system of FIG. 6 utilizes the sameorthogonally-related X axis 72, Y axis 76, and Z 74 as the Cartesiancoordinate system of FIGS. 3-5 to define locations on the airfoil shape110 for both the suction side profile 112 and the pressure side profile114 along the length L of the airfoil 82.

The X axis 72 and the Y axis 76 lie parallel to the base 60, asillustrated in the previous figures. In some embodiments, a positive Xcoordinate value is axial in the downstream axial direction 38 towardthe aft, for example the exhaust outlet 28 of the multi-stage axialcompressor 20. In some embodiments, a positive Y coordinate value isdirected normal to the X axis 72. A positive Z coordinate value isdirected radially from the X axis 72 and the Y axis 76 outward towardtip 68 of the airfoil 82, which is towards the static casing 48 of themulti-stage axial compressor 20 for rotor blades 44, and directedradially inward towards the shaft 30 of the multi-stage axial compressor20 for stator vanes 50.

By defining X and Y coordinate values at selected locations in a Zdirection normal to the X-Y plane, the airfoil shape 110, with itssuction side profile 112 and pressure side profile 114, may be defined,for example, by connecting each X and Y coordinate value to adjacent Xand Y coordinate values with smooth continuing arcs. The suction sideprofile 112 is joined to the pressure side profile 114, as shown in FIG.6, to define the airfoil shape 110. The airfoil shapes 110 (e.g.,sections) of the airfoil 82 at various surface locations (e.g., heights)between the Z coordinate values may be determined by smoothly connectingthe adjacent (e.g., “stacked”) airfoil shapes 110 to one another, thusforming the airfoil 82. It may be appreciated that the airfoil shape 110of the airfoil 82 may change from the base 60 to the tip 68. Forexample, adjacent airfoil shapes 110 may taper or expand in one or moredirections (e.g., X axis 72, Y axis 76), adjacent airfoil shapes 110 mayrotate about an axis (e.g., Z axis 74) in a clockwise direction or acounter-clockwise direction, or any combination thereof. It is also tobe noted that TABLE I values represent the Cartesian coordinate valuesfor the airfoil 82 at ambient, non-operating or non-hot conditions.Additionally, TABLE I values represent the Cartesian coordinate valuesfor an uncoated airfoil (i.e., without coatings 120). For a coatedairfoil, a thickness t of the coating 120 may be added to each of the X,Y values of TABLE I below.

The X, Y, and Z coordinate values of TABLE I below are non-dimensionalvalues convertible to dimensional distances with the scale factor F.That is, the X, Y, and Z values of TABLE I may be scaled as a functionof the same scale factor F (e.g., constant or number) to provide ascaled-up or a scaled-down airfoil. Thus, TABLE I defines therelationships between the X, Y, and Z coordinate values withoutspecifying the units of measure (e.g., dimensional units) for anembodiment of the airfoil 82. Accordingly, while different scale factorsF may be applied to the X, Y, and Z coordinate values of TABLE I todefine different embodiments of the airfoil 82, each embodiment of theairfoil 82 regardless of the particular scale factor F is considered tobe defined by the X, Y, and Z coordinate values of TABLE I. For example,the X, Y, and Z coordinate values of TABLE I define a first embodimentof the airfoil 82 formed with a 1:1 inch scale factor F, a secondembodiment of the airfoil 82 formed with a 1:2 inch scale factor F, anda third embodiment of the airfoil 82 formed with a 1:1 cm scale factorF. It may be appreciated that any scale factor F may be used with the X,Y, and Z coordinate values of TABLE I, according to the designconsiderations of a particular embodiment.

The TABLE I values below are computer-generated and shown to fivedecimal places. However, certain values in TABLE I may be shown to lessthan five decimal places (e.g., 0, 1, 2, 3, or 4 decimal places),because the values are rounded to significant figures, the additionaldecimal places would merely show trailing zeroes, or a combinationthereof. Accordingly, in certain embodiments, any values having lessthan five decimal places may be shown with trailing zeroes out to 1, 2,3, 4, or 5 decimal places. Furthermore, in some embodiments and in viewof manufacturing constraints, actual values useful for forming theairfoil 82 are may be considered valid to fewer (e.g., one, two, three,or four) decimal places for determining the airfoil shape 110 of theairfoil 82. Further, there are typical manufacturing tolerances whichmay be accounted for in the airfoil shape 110. Accordingly, the X, Y,and Z values given in TABLE I are for the airfoil shape 110 of a nominalairfoil. It will therefore be appreciated that plus or minus typicalmanufacturing tolerances are applicable to these X, Y, and Z values andthat an airfoil 82 having a profile substantially in accordance withthose values includes such tolerances. For example, in certainembodiments, a manufacturing tolerance of about ±between 0.001 to 0.20inches (e.g., between 0.025 to 5 mm) is within design limits for theairfoil 82, and a manufacturing tolerance of about ±0.0008 to 0.1 inches(e.g., 0.02 to 2.5 mm) may be maintained during manufacturing.Accordingly, the values of X and Y carried to three decimal places andhaving a manufacturing tolerance about ±0.010 inches (0.25 mm) andpreferably about ±0.008 inches (0.20 mm) is acceptable to define theairfoil shape 110 of the airfoil 82 at each radial position (e.g., Zcoordinate, height) throughout its entire length. As used herein, anyreference to Cartesian coordinate values of X, Y, and Z as set forth inTABLE I to a maximum of N decimal places is intended to include: (1)values to N decimal places if shown in TABLE I with N or greater decimalplaces, and (2) values to less than N decimal places if shown in TABLE 1with less than N decimal places, wherein N may be 0, 1, 2, 3, 4, or 5.For example, any reference to Cartesian coordinate values of X, Y, and Zas set forth in TABLE I to a maximum of three (3) decimal places isintended to include: (1) values to three (3) decimal places if shown inTABLE I with three (3) or greater decimal places, and (2) values to lessthan three (3) decimal places if shown in TABLE 1 with less than three(3) decimal places (e.g., 0, 1, or 2 decimal places). Furthermore, anyreference to Cartesian coordinate values of X, Y, and Z as set forth inTABLE I all carried to N decimal places is intended to include: (1)values to N decimal places if shown in TABLE I with N or greater decimalplaces, and (2) values with trailing zeros to N decimal places if shownin TABLE 1 with less than N decimal places, wherein N may be 0, 1, 2, 3,4, or 5.

As noted previously, the airfoil 82 may also be coated for protectionagainst corrosion, erosion, wear, and oxidation after the airfoil 82 ismanufactured, according to the values of TABLE I and within thetolerances explained above. For example, the coating region 120 mayinclude one or more corrosion resistant layers, erosion resistantlayers, wear resistant layers, oxidation resistant or anti-oxidationlayers, or any combination thereof. An anti-corrosion coating may beprovided with an average thickness t of 0.008 inches (0.20 mm), between0.001 and 0.1 inches (between 0.25 and 2.5 mm), between, 0.0001 and 1inches or more (between 0.0025 and 2.5 mm or more). For example, incertain embodiments, the coating 120 may increase X and Y values of asuction side in TABLE I by no greater than approximately 3.5 mm along afirst suction portion, a first pressure portion, or both. It is to benoted that additional anti-oxidation coatings 120 may be provided, suchas overcoats.

TABLE I Pressure Surface Suction Surface N X Y Z X Y Z 1 −1.49059−1.89340 18.60080 1.81098 1.18399 18.60080 2 −1.48974 −1.89373 18.600801.81061 1.18540 18.60080 3 −1.48797 −1.89424 18.60080 1.80979 1.1876818.60080 4 −1.48432 −1.89468 18.60080 1.80676 1.19262 18.60080 5−1.47707 −1.89355 18.60080 1.79895 1.19820 18.60080 6 −1.46667 −1.8886918.60080 1.78224 1.19818 18.60080 7 −1.45041 −1.87590 18.60080 1.760771.19426 18.60080 8 −1.43156 −1.85574 18.60080 1.73216 1.18886 18.60080 9−1.40903 −1.82662 18.60080 1.69408 1.18140 18.60080 10 −1.38264 −1.7888918.60080 1.64655 1.17164 18.60080 11 −1.34895 −1.73944 18.60080 1.584941.15819 18.60080 12 −1.31059 −1.68202 18.60080 1.51405 1.14174 18.6008013 −1.27006 −1.62051 18.60080 1.43867 1.12321 18.60080 14 −1.22471−1.55116 18.60080 1.35893 1.10217 18.60080 15 −1.17443 −1.47403 18.600801.27030 1.07684 18.60080 16 −1.11910 −1.38920 18.60080 1.16842 1.0450418.60080 17 −1.06095 −1.30072 18.60080 1.06284 1.00894 18.60080 18−0.99951 −1.20890 18.60080 0.95381 0.96809 18.60080 19 −0.93426 −1.1141018.60080 0.84158 0.92212 18.60080 20 −0.86473 −1.01667 18.60080 0.726410.87069 18.60080 21 −0.79058 −0.91692 18.60080 0.60853 0.81359 18.6008022 −0.71154 −0.81510 18.60080 0.48808 0.75080 18.60080 23 −0.62742−0.71144 18.60080 0.36514 0.68239 18.60080 24 −0.53807 −0.60613 18.600800.23990 0.60827 18.60080 25 −0.44650 −0.50275 18.60080 0.11688 0.5305018.60080 26 −0.35290 −0.40120 18.60080 −0.00347 0.44867 18.60080 27−0.25746 −0.30139 18.60080 −0.12073 0.36246 18.60080 28 −0.16045−0.20309 18.60080 −0.23442 0.27161 18.60080 29 −0.06229 −0.1059418.60080 −0.34415 0.17601 18.60080 30 0.03659 −0.00952 18.60080 −0.449710.07583 18.60080 31 0.13613 0.08621 18.60080 −0.55113 −0.02854 18.6008032 0.23649 0.18108 18.60080 −0.64845 −0.13675 18.60080 33 0.338020.27470 18.60080 −0.74166 −0.24852 18.60080 34 0.44123 0.36646 18.60080−0.83071 −0.36363 18.60080 35 0.54665 0.45567 18.60080 −0.91553 −0.4818918.60080 36 0.65103 0.53890 18.60080 −0.99349 −0.59900 18.60080 370.75426 0.61608 18.60080 −1.06507 −0.71444 18.60080 38 0.85609 0.6873518.60080 −1.13066 −0.82782 18.60080 39 0.95625 0.75287 18.60080 −1.19057−0.93882 18.60080 40 1.05448 0.81282 18.60080 −1.24509 −1.04715 18.6008041 1.15049 0.86748 18.60080 −1.29441 −1.15262 18.60080 42 1.243950.91723 18.60080 −1.33862 −1.25507 18.60080 43 1.33453 0.96254 18.60080−1.37773 −1.35437 18.60080 44 1.41358 0.99997 18.60080 −1.41045 −1.4457118.60080 45 1.48490 1.03220 18.60080 −1.43764 −1.52870 18.60080 461.55249 1.06147 18.60080 −1.45965 −1.60313 18.60080 47 1.61626 1.0879618.60080 −1.47806 −1.67353 18.60080 48 1.67180 1.11023 18.60080 −1.49204−1.73503 18.60080 49 1.71466 1.12704 18.60080 −1.50132 −1.78264 18.6008050 1.74900 1.14034 18.60080 −1.50645 −1.82110 18.60080 51 1.774791.15025 18.60080 −1.50733 −1.85018 18.60080 52 1.79414 1.15763 18.60080−1.50463 −1.87181 18.60080 53 1.80724 1.16650 18.60080 −1.50057 −1.8832018.60080 54 1.81097 1.17485 18.60080 −1.49613 −1.88954 18.60080 551.81145 1.18034 18.60080 −1.49315 −1.89202 18.60080 56 1.81123 1.1826318.60080 −1.49148 −1.89299 18.60080 57 −1.50393 −1.82567 18.491071.80812 1.14428 18.49107 58 −1.50310 −1.82602 18.49107 1.80776 1.1456618.49107 59 −1.50137 −1.82658 18.49107 1.80694 1.14790 18.49107 60−1.49780 −1.82715 18.49107 1.80393 1.15275 18.49107 61 −1.49063 −1.8263318.49107 1.79621 1.15818 18.49107 62 −1.48022 −1.82195 18.49107 1.779771.15802 18.49107 63 −1.46378 −1.80995 18.49107 1.75864 1.15419 18.4910764 −1.44459 −1.79072 18.49107 1.73049 1.14894 18.49107 65 −1.42155−1.76274 18.49107 1.69301 1.14170 18.49107 66 −1.39452 −1.72639 18.491071.64623 1.13224 18.49107 67 −1.36004 −1.67864 18.49107 1.58557 1.1192418.49107 68 −1.32079 −1.62315 18.49107 1.51577 1.10339 18.49107 69−1.27937 −1.56366 18.49107 1.44152 1.08560 18.49107 70 −1.23300 −1.4965818.49107 1.36294 1.06544 18.49107 71 −1.18152 −1.42200 18.49107 1.275571.04119 18.49107 72 −1.12483 −1.34002 18.49107 1.17508 1.01079 18.4910773 −1.06521 −1.25456 18.49107 1.07090 0.97627 18.49107 74 −1.00215−1.16597 18.49107 0.96323 0.93722 18.49107 75 −0.93519 −1.07462 18.491070.85233 0.89327 18.49107 76 −0.86395 −0.98080 18.49107 0.73841 0.8441218.49107 77 −0.78812 −0.88481 18.49107 0.62168 0.78958 18.49107 78−0.70752 −0.78686 18.49107 0.50226 0.72965 18.49107 79 −0.62197 −0.6871418.49107 0.38021 0.66441 18.49107 80 −0.53136 −0.58583 18.49107 0.255710.59375 18.49107 81 −0.43874 −0.48635 18.49107 0.13324 0.51961 18.4910782 −0.34429 −0.38861 18.49107 0.01322 0.44157 18.49107 83 −0.24819−0.29250 18.49107 −0.10392 0.35930 18.49107 84 −0.15068 −0.1978118.49107 −0.21778 0.27252 18.49107 85 −0.05211 −0.10422 18.49107−0.32799 0.18116 18.49107 86 0.04717 −0.01138 18.49107 −0.43433 0.0853218.49107 87 0.14709 0.08076 18.49107 −0.53677 −0.01467 18.49107 880.24776 0.17208 18.49107 −0.63531 −0.11852 18.49107 89 0.34948 0.2622418.49107 −0.72991 −0.22597 18.49107 90 0.45270 0.35067 18.49107 −0.82050−0.33681 18.49107 91 0.55790 0.43672 18.49107 −0.90699 −0.45088 18.4910792 0.66184 0.51709 18.49107 −0.98666 −0.56403 18.49107 93 0.764440.59170 18.49107 −1.05993 −0.67577 18.49107 94 0.86546 0.66067 18.49107−1.12715 −0.78568 18.49107 95 0.96469 0.72415 18.49107 −1.18866 −0.8934418.49107 96 1.06189 0.78229 18.49107 −1.24472 −0.99874 18.49107 971.15679 0.83536 18.49107 −1.29556 −1.10136 18.49107 98 1.24911 0.8836918.49107 −1.34128 −1.20114 18.49107 99 1.33851 0.92775 18.49107 −1.38189−1.29795 18.49107 100 1.41649 0.96421 18.49107 −1.41603 −1.3870818.49107 101 1.48681 0.99563 18.49107 −1.44448 −1.46812 18.49107 1021.55343 1.02422 18.49107 −1.46764 −1.54088 18.49107 103 1.61625 1.0501318.49107 −1.48719 −1.60973 18.49107 104 1.67096 1.07196 18.49107−1.50223 −1.66992 18.49107 105 1.71316 1.08845 18.49107 −1.51237−1.71655 18.49107 106 1.74697 1.10151 18.49107 −1.51821 −1.7542618.49107 107 1.77235 1.11124 18.49107 −1.51964 −1.78284 18.49107 1081.79140 1.11850 18.49107 −1.51736 −1.80416 18.49107 109 1.80440 1.1270918.49107 −1.51354 −1.81543 18.49107 110 1.80811 1.13529 18.49107−1.50928 −1.82174 18.49107 111 1.80859 1.14069 18.49107 −1.50641−1.82424 18.49107 112 1.80837 1.14294 18.49107 −1.50479 −1.8252418.49107 113 −1.52127 −1.73868 18.34904 1.80448 1.09290 18.34904 114−1.52046 −1.73905 18.34904 1.80413 1.09425 18.34904 115 −1.51880−1.73966 18.34904 1.80332 1.09645 18.34904 116 −1.51532 −1.7403618.34904 1.80035 1.10118 18.34904 117 −1.50826 −1.73984 18.34904 1.792751.10644 18.34904 118 −1.49789 −1.73597 18.34904 1.77664 1.10618 18.34904119 −1.48132 −1.72487 18.34904 1.75593 1.10249 18.34904 120 −1.46181−1.70676 18.34904 1.72836 1.09744 18.34904 121 −1.43822 −1.6802218.34904 1.69162 1.09049 18.34904 122 −1.41043 −1.64560 18.34904 1.645781.08144 18.34904 123 −1.37501 −1.60003 18.34904 1.58631 1.06903 18.34904124 −1.33465 −1.54705 18.34904 1.51786 1.05398 18.34904 125 −1.29201−1.49024 18.34904 1.44501 1.03712 18.34904 126 −1.24419 −1.4262118.34904 1.36790 1.01804 18.34904 127 −1.19098 −1.35513 18.34904 1.282130.99512 18.34904 128 −1.13230 −1.27704 18.34904 1.18343 0.96638 18.34904129 −1.07054 −1.19573 18.34904 1.08102 0.93376 18.34904 130 −1.00520−1.11156 18.34904 0.97510 0.89690 18.34904 131 −0.93592 −1.0248418.34904 0.86587 0.85550 18.34904 132 −0.86239 −0.93586 18.34904 0.753500.80931 18.34904 133 −0.78440 −0.84482 18.34904 0.63816 0.75818 18.34904134 −0.70181 −0.75192 18.34904 0.51995 0.70209 18.34904 135 −0.61449−0.65730 18.34904 0.39898 0.64104 18.34904 136 −0.52235 −0.5611318.34904 0.27540 0.57485 18.34904 137 −0.42849 −0.46663 18.34904 0.153690.50530 18.34904 138 −0.33308 −0.37370 18.34904 0.03419 0.43201 18.34904139 −0.23628 −0.28221 18.34904 −0.08268 0.35460 18.34904 140 −0.13831−0.19198 18.34904 −0.19659 0.27290 18.34904 141 −0.03942 −0.1027618.34904 −0.30724 0.18685 18.34904 142 0.06015 −0.01429 18.34904−0.41440 0.09648 18.34904 143 0.16036 0.07345 18.34904 −0.51800 0.0020518.34904 144 0.26129 0.16036 18.34904 −0.61798 −0.09621 18.34904 1450.36317 0.24615 18.34904 −0.71426 −0.19809 18.34904 146 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13.70849 1.77766 0.30008 13.70849 901 −1.56251−1.69264 13.70849 1.77056 0.30358 13.70849 902 −1.55335 −1.6891413.70849 1.75665 0.30195 13.70849 903 −1.53789 −1.68057 13.70849 1.738830.29889 13.70849 904 −1.51839 −1.66734 13.70849 1.71510 0.29466 13.70849905 −1.49331 −1.64838 13.70849 1.68350 0.28875 13.70849 906 −1.46257−1.62390 13.70849 1.64407 0.28102 13.70849 907 −1.42313 −1.5914413.70849 1.59291 0.27048 13.70849 908 −1.37781 −1.55376 13.70849 1.533980.25782 13.70849 909 −1.32936 −1.51369 13.70849 1.47126 0.24372 13.70849910 −1.27477 −1.46872 13.70849 1.40478 0.22804 13.70849 911 −1.21396−1.41894 13.70849 1.33070 0.20957 13.70849 912 −1.14681 −1.3644913.70849 1.24525 0.18695 13.70849 913 −1.07626 −1.30800 13.70849 1.156280.16194 13.70849 914 −1.00219 −1.24962 13.70849 1.06387 0.13436 13.70849915 −0.92451 −1.18949 13.70849 0.96811 0.10402 13.70849 916 −0.84312−1.12774 13.70849 0.86909 0.07072 13.70849 917 −0.75792 −1.0645113.70849 0.76692 0.03425 13.70849 918 −0.66884 −0.99994 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0.0252713.70849 −1.10668 −1.12252 13.70849 937 1.19919 0.06193 13.70849−1.17512 −1.19046 13.70849 938 1.28285 0.09613 13.70849 −1.23935−1.25691 13.70849 939 1.36320 0.12801 13.70849 −1.29951 −1.3216713.70849 940 1.43284 0.15494 13.70849 −1.35307 −1.38158 13.70849 9411.49533 0.17854 13.70849 −1.40016 −1.43647 13.70849 942 1.55432 0.2002813.70849 −1.44119 −1.48597 13.70849 943 1.60981 0.22017 13.70849−1.47894 −1.53295 13.70849 944 1.65802 0.23704 13.70849 −1.51082−1.57433 13.70849 945 1.69515 0.24990 13.70849 −1.53439 −1.6068713.70849 946 1.72487 0.26016 13.70849 −1.55234 −1.63353 13.70849 9471.74715 0.26786 13.70849 −1.56461 −1.65428 13.70849 948 1.76386 0.2736413.70849 −1.57231 −1.67063 13.70849 949 1.77643 0.27903 13.70849−1.57527 −1.68022 13.70849 950 1.78088 0.28540 13.70849 −1.57582−1.68660 13.70849 951 1.78174 0.29001 13.70849 −1.57511 −1.6897213.70849 952 1.78165 0.29197 13.70849 −1.57430 −1.69110 13.70849 953−1.57254 −1.64631 13.48192 1.77262 0.35535 13.48192 954 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−0.84798 −1.07390 13.48192 0.86226 0.12796 13.48192973 −0.76309 −1.01020 13.48192 0.76048 0.09065 13.48192 974 −0.67429−0.94519 13.48192 0.65572 0.04988 13.48192 975 −0.58153 −0.8789313.48192 0.54811 0.00543 13.48192 976 −0.48480 −0.81150 13.48192 0.43779−0.04291 13.48192 977 −0.38732 −0.74514 13.48192 0.32853 −0.0936013.48192 978 −0.28917 −0.67979 13.48192 0.22035 −0.14655 13.48192 979−0.19040 −0.61538 13.48192 0.11326 −0.20167 13.48192 980 −0.09102−0.55191 13.48192 0.00733 −0.25901 13.48192 981 0.00899 −0.4894413.48192 −0.09734 −0.31859 13.48192 982 0.10963 −0.42797 13.48192−0.20070 −0.38042 13.48192 983 0.21089 −0.36755 13.48192 −0.30274−0.44442 13.48192 984 0.31280 −0.30823 13.48192 −0.40339 −0.5105713.48192 985 0.41544 −0.25018 13.48192 −0.50257 −0.57892 13.48192 9860.51891 −0.19363 13.48192 −0.60018 −0.64948 13.48192 987 0.62327−0.13872 13.48192 −0.69611 −0.72231 13.48192 988 0.72495 −0.0872113.48192 −0.78716 −0.79489 13.48192 989 0.82385 −0.03892 13.48192−0.87339 −0.86700 13.48192 990 0.91986 0.00629 13.48192 −0.95493−0.93843 13.48192 991 1.01290 0.04858 13.48192 −1.03190 −1.0089413.48192 992 1.10288 0.08807 13.48192 −1.10446 −1.07829 13.48192 9931.18972 0.12492 13.48192 −1.17274 −1.14628 13.48192 994 1.27336 0.1592313.48192 −1.23685 −1.21274 13.48192 995 1.35373 0.19115 13.48192−1.29693 −1.27748 13.48192 996 1.42340 0.21805 13.48192 −1.35045−1.33735 13.48192 997 1.48593 0.24159 13.48192 −1.39758 −1.3921313.48192 998 1.54498 0.26325 13.48192 −1.43870 −1.44149 13.48192 9991.60051 0.28304 13.48192 −1.47659 −1.48829 13.48192 1000 1.64878 0.2998213.48192 −1.50865 −1.52948 13.48192 1001 1.68596 0.31258 13.48192−1.53243 −1.56183 13.48192 1002 1.71571 0.32275 13.48192 −1.55055−1.58835 13.48192 1003 1.73803 0.33037 13.48192 −1.56295 −1.6089913.48192 1004 1.75477 0.33608 13.48192 −1.57077 −1.62527 13.48192 10051.76741 0.34132 13.48192 −1.57384 −1.63481 13.48192 1006 1.77197 0.3476113.48192 −1.57451 −1.64118 13.48192 1007 1.77289 0.35222 13.48192−1.57386 −1.64431 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1.14055 0.27433 13.27660 1026 −1.00832 −1.14637 13.276601.04879 0.24563 13.27660 1027 −0.93133 −1.08550 13.27660 0.95376 0.2140113.27660 1028 −0.85058 −1.02308 13.27660 0.85556 0.17931 13.27660 1029−0.76598 −0.95924 13.27660 0.75428 0.14135 13.27660 1030 −0.67746−0.89407 13.27660 0.65004 0.09993 13.27660 1031 −0.58499 −0.8276613.27660 0.54297 0.05485 13.27660 1032 −0.48857 −0.76004 13.276600.43323 0.00586 13.27660 1033 −0.39143 −0.69347 13.27660 0.32457−0.04549 13.27660 1034 −0.29364 −0.62785 13.27660 0.21701 −0.0991013.27660 1035 −0.19526 −0.56311 13.27660 0.11056 −0.15488 13.27660 1036−0.09630 −0.49926 13.27660 0.00529 −0.21285 13.27660 1037 0.00326−0.43636 13.27660 −0.09875 −0.27301 13.27660 1038 0.10344 −0.3744513.27660 −0.20151 −0.33533 13.27660 1039 0.20426 −0.31359 13.27660−0.30298 −0.39972 13.27660 1040 0.30576 −0.25385 13.27660 −0.40312−0.46616 13.27660 1041 0.40801 −0.19542 13.27660 −0.50184 −0.5347013.27660 1042 0.51112 −0.13852 13.27660 −0.59905 −0.60536 13.27660 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−1.5779013.27660 1061 1.75732 0.39693 13.27660 −1.57221 −1.58739 13.27660 10621.76197 0.40314 13.27660 −1.57296 −1.59374 13.27660 1063 1.76293 0.4077313.27660 −1.57236 −1.59687 13.27660 1064 1.76286 0.40969 13.27660−1.57159 −1.59827 13.27660 1065 −1.56696 −1.51382 12.88459 1.736540.50907 12.88459 1066 −1.56635 −1.51432 12.88459 1.73626 0.5102312.88459 1067 −1.56495 −1.51499 12.88459 1.73556 0.51209 12.88459 1068−1.56186 −1.51534 12.88459 1.73273 0.51590 12.88459 1069 −1.55576−1.51405 12.88459 1.72555 0.51900 12.88459 1070 −1.54683 −1.5101212.88459 1.71180 0.51698 12.88459 1071 −1.53181 −1.50099 12.884591.69419 0.51375 12.88459 1072 −1.51290 −1.48714 12.88459 1.67073 0.5092912.88459 1073 −1.48865 −1.46741 12.88459 1.63950 0.50309 12.88459 1074−1.45893 −1.44205 12.88459 1.60054 0.49497 12.88459 1075 −1.42066−1.40864 12.88459 1.55001 0.48387 12.88459 1076 −1.37652 −1.3700712.88459 1.49185 0.47044 12.88459 1077 −1.32923 −1.32917 12.884591.42997 0.45543 12.88459 1078 −1.27586 −1.28336 12.88459 1.36442 0.4386912.88459 1079 −1.21634 −1.23272 12.88459 1.29142 0.41899 12.88459 1080−1.15053 −1.17740 12.88459 1.20726 0.39488 12.88459 1081 −1.08132−1.12007 12.88459 1.11970 0.36821 12.88459 1082 −1.00861 −1.0608412.88459 1.02884 0.33878 12.88459 1083 −0.93229 −0.99986 12.884590.93478 0.30637 12.88459 1084 −0.85228 −0.93724 12.88459 0.83763 0.2707512.88459 1085 −0.76851 −0.87311 12.88459 0.73751 0.23175 12.88459 1086−0.68092 −0.80754 12.88459 0.63454 0.18917 12.88459 1087 −0.58951−0.74057 12.88459 0.52886 0.14280 12.88459 1088 −0.49426 −0.6722312.88459 0.42063 0.09242 12.88459 1089 −0.39840 −0.60475 12.884590.31355 0.03963 12.88459 1090 −0.30200 −0.53805 12.88459 0.20764−0.01548 12.88459 1091 −0.20510 −0.47207 12.88459 0.10293 −0.0728312.88459 1092 −0.10771 −0.40683 12.88459 −0.00054 −0.13238 12.88459 1093−0.00975 −0.34244 12.88459 −0.10276 −0.19406 12.88459 1094 0.08886−0.27904 12.88459 −0.20374 −0.25774 12.88459 1095 0.18818 −0.2167712.88459 −0.30351 −0.32331 12.88459 1096 0.28828 −0.15577 12.88459−0.40205 −0.39072 12.88459 1097 0.38927 −0.09625 12.88459 −0.49928−0.45999 12.88459 1098 0.49124 −0.03842 12.88459 −0.59514 −0.5311512.88459 1099 0.59422 0.01760 12.88459 −0.68954 −0.60424 12.88459 11000.69467 0.07004 12.88459 −0.77930 −0.67677 12.88459 1101 0.79248 0.1190812.88459 −0.86451 −0.74858 12.88459 1102 0.88753 0.16486 12.88459−0.94524 −0.81948 12.88459 1103 0.97975 0.20750 12.88459 −1.02163−0.88927 12.88459 1104 1.06903 0.24715 12.88459 −1.09379 −0.9577712.88459 1105 1.15529 0.28395 12.88459 −1.16184 −1.02478 12.88459 11061.23843 0.31807 12.88459 −1.22591 −1.09015 12.88459 1107 1.31838 0.3496812.88459 −1.28611 −1.15371 12.88459 1108 1.38772 0.37621 12.88459−1.33991 −1.21237 12.88459 1109 1.44999 0.39933 12.88459 −1.38749−1.26592 12.88459 1110 1.50882 0.42052 12.88459 −1.42910 −1.3141212.88459 1111 1.56417 0.43979 12.88459 −1.46757 −1.35976 12.88459 11121.61231 0.45602 12.88459 −1.50027 −1.39984 12.88459 1113 1.64941 0.4682712.88459 −1.52470 −1.43126 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11.87050 −1.55629 −1.43606 11.87050 13441.69585 0.73991 11.87050 −1.55559 −1.43749 11.87050 1345 −1.55465−1.45817 11.67269 1.68597 0.78572 11.67269 1346 −1.55401 −1.4586511.67269 1.68571 0.78690 11.67269 1347 −1.55254 −1.45925 11.672691.68503 0.78880 11.67269 1348 −1.54938 −1.45938 11.67269 1.68219 0.7926811.67269 1349 −1.54325 −1.45776 11.67269 1.67486 0.79570 11.67269 1350−1.53431 −1.45342 11.67269 1.66094 0.79345 11.67269 1351 −1.51941−1.44353 11.67269 1.64311 0.78997 11.67269 1352 −1.50084 −1.4285511.67269 1.61937 0.78516 11.67269 1353 −1.47722 −1.40723 11.672691.58779 0.77842 11.67269 1354 −1.44816 −1.38007 11.67269 1.54842 0.7695111.67269 1355 −1.41046 −1.34470 11.67269 1.49743 0.75709 11.67269 1356−1.36699 −1.30384 11.67269 1.43886 0.74171 11.67269 1357 −1.32058−1.26030 11.67269 1.37670 0.72418 11.67269 1358 −1.26827 −1.2114211.67269 1.31104 0.70421 11.67269 1359 −1.21005 −1.15722 11.672691.23818 0.68027 11.67269 1360 −1.14586 −1.09775 11.67269 1.15448 0.6505711.67269 1361 −1.07852 −1.03583 11.67269 1.06776 0.61742 11.67269 1362−1.00795 −0.97157 11.67269 0.97812 0.58067 11.67269 1363 −0.93404−0.90505 11.67269 0.88567 0.54019 11.67269 1364 −0.85671 −0.8363911.67269 0.79053 0.49587 11.67269 1365 −0.77586 −0.76573 11.672690.69279 0.44763 11.67269 1366 −0.69136 −0.69319 11.67269 0.59257 0.3953811.67269 1367 −0.60311 −0.61891 11.67269 0.48998 0.33900 11.67269 1368−0.51104 −0.54302 11.67269 0.38515 0.27835 11.67269 1369 −0.41817−0.46812 11.67269 0.28163 0.21551 11.67269 1370 −0.32450 −0.3942011.67269 0.17936 0.15065 11.67269 1371 −0.23009 −0.32125 11.672690.07835 0.08384 11.67269 1372 −0.13492 −0.24927 11.67269 −0.021390.01516 11.67269 1373 −0.03904 −0.17826 11.67269 −0.11992 −0.0552611.67269 1374 0.05743 −0.10805 11.67269 −0.21725 −0.12732 11.67269 13750.15452 −0.03869 11.67269 −0.31337 −0.20099 11.67269 1376 0.252360.02961 11.67269 −0.40819 −0.27632 11.67269 1377 0.35105 0.0966711.67269 −0.50163 −0.35336 11.67269 1378 0.45069 0.16231 11.67269−0.59365 −0.43209 11.67269 1379 0.55132 0.22641 11.67269 −0.68425−0.51246 11.67269 1380 0.64957 0.28683 11.67269 −0.77045 −0.5916711.67269 1381 0.74534 0.34366 11.67269 −0.85241 −0.66949 11.67269 13820.83857 0.39695 11.67269 −0.93032 −0.74572 11.67269 1383 0.92920 0.4467411.67269 −1.00434 −0.82013 11.67269 1384 1.01717 0.49308 11.67269−1.07461 −0.89257 11.67269 1385 1.10241 0.53603 11.67269 −1.14128−0.96287 11.67269 1386 1.18485 0.57568 11.67269 −1.20450 −1.0308611.67269 1387 1.26440 0.61213 11.67269 −1.26437 −1.09646 11.67269 13881.33365 0.64236 11.67269 −1.31827 −1.15657 11.67269 1389 1.39607 0.6683611.67269 −1.36640 −1.21100 11.67269 1390 1.45521 0.69186 11.67269−1.40890 −1.25965 11.67269 1391 1.51102 0.71293 11.67269 −1.44840−1.30554 11.67269 1392 1.55966 0.73045 11.67269 −1.48231 −1.3455811.67269 1393 1.59722 0.74353 11.67269 −1.50820 −1.37656 11.67269 13941.62734 0.75379 11.67269 −1.52842 −1.40174 11.67269 1395 1.64997 0.7613711.67269 −1.54242 −1.42150 11.67269 1396 1.66696 0.76699 11.67269−1.55143 −1.43726 11.67269 1397 1.67994 0.77189 11.67269 −1.55517−1.44662 11.67269 1398 1.68494 0.77795 11.67269 −1.55633 −1.4529611.67269 1399 1.68611 0.78255 11.67269 −1.55592 −1.45614 11.67269 14001.68611 0.78454 11.67269 −1.55518 −1.45757 11.67269

It is noted that the first column of TABLE I lists X coordinate valuesof the pressure side at each respective Z coordinate value of the thirdcolumn, the second column lists Y coordinate values of the pressure sideat each respective Z coordinate value of the third column, the fourthcolumn lists X coordinate values of the suction side at each respectiveZ coordinate value of the sixth column, and the fifth column lists Ycoordinate values of the suction side at each respective Z coordinatevalue of the sixth column. The Z coordinate values of the third columnand the sixth column are equal to each other for each respective row. Asset forth in TABLE I, at each respective Z coordinate value, the airfoilshape 110 of the airfoil 82 (e.g., a cross-sectional profile takenthrough line 6-6 of FIGS. 3, 4, and 5) is defined by multiple sets ofCartesian coordinate values of X, Y, and Z for both the suction side 62(e.g., suction side profile 112) and the pressure side 64 (e.g.,pressure side profile 114). For example, at each respective Z coordinatevalue, the suction side profile 112 of the suction side 62 may bedefined by at least equal to or greater than 10, 15, 20, 25, 30, 35, 40,45, 50, or 55 (e.g., 56) sets of Cartesian coordinate values of X, Y,and Z. Similarly, at each respective Z coordinate value, the pressureside profile 114 of the pressure side 64 may be defined by at leastequal to or greater than 10, 15, 20, 25, 30, 35, 40, 45, 50, or 55(e.g., 56) sets of Cartesian coordinate values of X, Y, and Z.Furthermore, in the Z direction along the Z axis 74, the airfoil profileof the airfoil 82 may be defined by multiple sets of Cartesiancoordinate values of X, Y, and Z at multiple Cartesian coordinate valuesof Z, such as at least equal to or greater than 2, 3, 4, 5, 6, 7, 8, 9,10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26, 27,28, 29, 30, or more Cartesian coordinate values of Z.

As noted above, the Cartesian coordinate values of X, Y, and Z as setforth in TABLE I may be non-dimensional values convertible todimensional distances. For example, the Cartesian coordinate values ofX, Y, and Z may be multiplied by a scale factor F (e.g., F equal to 1,greater than 1, or less than 1) to obtain the desired dimensionaldistances. In certain embodiments, a nominal airfoil profile of theairfoil 82 may be partially or entirely (e.g., all or part of thesuction side 62, all or part of the pressure side 64, or a combinationthereof) defined by the Cartesian coordinate values of X, Y, and Z asset forth in TABLE I. The nominal airfoil profile of the airfoil 82 alsomay be covered by the coating 120, which increases the X and Y values asset forth in TABLE I.

For example, the airfoil 82 may include a first suction portion (e.g.,80) of the nominal airfoil profile substantially in accordance withCartesian coordinate values of X, Y, and Z of the suction side 62 as setforth in TABLE I, wherein the X and Y values of the suction side 62 arecoordinate values that couple together (e.g., in a smooth continuousand/or curved manner) to define suction side sections of the firstsuction portion (e.g., 80) of the nominal airfoil profile at each Zcoordinate value, and the suction side sections of the first suctionportion (e.g., 80) of the nominal airfoil profile are coupled together(e.g., in a smooth continuous and/or curved manner) to define the firstsuction portion (e.g., 80). In such an embodiment, the airfoil 82 has anairfoil length L along the Z axis 74, and the first suction portion(e.g., 80) comprises a first portion length l along the Z axis asillustrated and described above with reference to FIG. 4. The firstportion length l is less than or equal to the airfoil length L. Thefirst portion length l may include greater than or equal to 2, 3, 4, 5,6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24,25, 26, 27, 28, 29, 30, or more Cartesian coordinate values of Z (e.g.,consecutive values of Z) in TABLE I. The first portion length l may beequal to or greater than approximately 5, 10, 15, 20, 25, 30, 35, 40,45, 50, 55, 60, 65, 70, 75, 80, 85, 90, 95, 99, or 100 percent of theairfoil length L.

By further example, the airfoil 82 may include a second suction portion(e.g., 80) of the nominal airfoil profile substantially in accordancewith the Cartesian coordinate values of X, Y, and Z of the suction side62 as set forth in TABLE I, wherein the X and Y values of the suctionside 62 are coordinate values that couple together (e.g., in a smoothcontinuous and/or curved manner) to define suction side sections of thesecond suction portion (e.g., 80) of the nominal airfoil profile at eachZ coordinate value, the suction side sections of the second suctionportion (e.g., 80) of the nominal airfoil profile are coupled together(e.g., in a smooth continuous and/or curved manner) to define the secondsuction portion (e.g., 80). In such an embodiment, the second suctionportion (e.g., 80) has a second portion length l along the Z axis, thesecond portion length l is less than or equal to the airfoil length L,and the first and second suction portions (e.g., 80, 102, 104, 106) areoffset from one another along the Z axis as illustrated and describedabove with reference to FIGS. 4 and 5. Again, the second portion lengthl may include greater than or equal to 2, 3, 4, 5, 6, 7, 8, 9, 10, 11,12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26, 27, 28, 29,30, or more Cartesian coordinate values of Z (e.g., consecutive valuesof Z) in TABLE I. The second portion length l may be equal to or greaterthan approximately 5, 10, 15, 20, 25, 30, 35, 40, 45, 50, 55, 60, 65,70, 75, 80, 85, 90, 95, 99, or 100 percent of the airfoil length L.Furthermore, the first and second suction portions (e.g., 80, 102, 104,106) may be separated by an offset distance of equal to or greater thanapproximately 5, 10, 15, 20, 25, 30, 35, 40, 45, 50, 55, 60, 65, 70, 75,80, 85, or 90 percent of the airfoil length L.

By further example, the airfoil 82 may include a first pressure portion(e.g., 80) of the nominal airfoil profile substantially in accordancewith the Cartesian coordinate values of X, Y, and Z of the pressure side64 as set forth in TABLE I, wherein the X and Y values of the pressureside 64 are coordinate values that couple together (e.g., in a smoothcontinuous and/or curved manner) to define pressure side sections of thefirst pressure portion (e.g., 80) of the nominal airfoil profile at eachZ coordinate value, the pressure side sections of the first pressureportion (e.g., 80) of the nominal airfoil profile are coupled together(e.g., in a smooth continuous and/or curved manner) to define the firstpressure portion (e.g., 80). In such an embodiment, the first pressureportion (e.g., 80) comprises a second portion length l along the Z axis,and the second portion length l is less than or equal to the airfoillength L as illustrated and described above with reference to FIG. 4.Similar to the first suction portion (e.g., 80), the second portionlength l of the first pressure portion (e.g., 80) may include greaterthan or equal to 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17,18, 19, 20, 21, 22, 23, 24, 25, 26, 27, 28, 29, 30, or more Cartesiancoordinate values of Z (e.g., consecutive values of Z) in TABLE I. Thesecond portion length l of the first pressure portion (e.g., 80) may beequal to or greater than approximately 5, 10, 15, 20, 25, 30, 35, 40,45, 50, 55, 60, 65, 70, 75, 80, 85, 90, 95, 99, or 100 percent of theairfoil length L. In certain embodiments, the first suction portion(e.g., 80) and the first pressure portion (e.g., 80) at least partiallyoverlap with one another along the Z axis.

For example, in certain embodiments, the first and second portionlengths l may be substantially the same, and the first and secondportion lengths l may start at a common distance d relative to the base60 of the airfoil 82 and extend toward the tip 68 of the airfoil 82.However, in some embodiments, the first and second portion lengths l maybe different from one another, the first and second portion lengths lmay start at different distances d relative to the base 60 of theairfoil 82, or a combination thereof. Additionally, the airfoil 82 mayinclude a second pressure portion (e.g., 80) of the nominal airfoilprofile substantially in accordance with the Cartesian coordinate valuesof X, Y, and Z of the pressure side 64 as set forth in TABLE I, whereinthe first and second pressure portions (e.g., 80, 102, 104, 106) areoffset from one another along the Z axis 74.

Technical effects of the disclosed embodiments include an airfoil havinga first suction portion of a nominal airfoil profile substantially inaccordance with Cartesian coordinate values of X, Y, and Z of a suctionside as set forth in TABLE I, wherein the X and Y values of the suctionside are coordinate values that couple together to define suction sidesections of the first suction portion of the nominal airfoil profile ateach Z coordinate value, the suction side sections of the first suctionportion of the nominal airfoil profile are coupled together to definethe first suction portion, the airfoil includes an airfoil length alonga Z axis, the first suction portion comprises a first portion lengthalong the Z axis, the first portion length is less than or equal to theairfoil length, and the Cartesian coordinate values of X, Y, and Z arenon-dimensional values convertible to dimensional distances (e.g.,instances in inches or mm).

This written description uses examples to disclose the subject matter,including the best mode, and also to enable any person skilled in theart to practice the subject matter, including making and using anydevices or systems and performing any incorporated methods. Thepatentable scope of the subject matter is defined by the claims, and mayinclude other examples that occur to those skilled in the art. Suchother examples are intended to be within the scope of the claims if theyhave structural elements that do not differ from the literal language ofthe claims, or if they include equivalent structural elements withinsubstantial differences from the literal language of the claims.

The invention claimed is:
 1. A system comprising: an airfoil comprisinga first suction portion of a nominal airfoil profile substantially inaccordance with Cartesian coordinate values of X, Y, and Z of a suctionside as set forth in TABLE I to a maximum of three decimal places,wherein the X and Y values of the suction side are coordinate valuesthat couple together to define suction side sections of the firstsuction portion of the nominal airfoil profile at each Z coordinatevalue, the suction side sections of the first suction portion of thenominal airfoil profile are coupled together to define the first suctionportion, the airfoil comprises an airfoil length along a Z axis, thefirst suction portion comprises a first portion length along the Z axis,the first portion length is less than or equal to the airfoil length,and the Cartesian coordinate values of X, Y, and Z are non-dimensionalvalues convertible to dimensional distances.
 2. The system of claim 1,wherein the airfoil comprises a second suction portion of the nominalairfoil profile substantially in accordance with the Cartesiancoordinate values of X, Y, and Z of the suction side as set forth inTABLE I to the maximum of three decimal places, wherein the X and Yvalues of the suction side are coordinate values that couple together todefine suction side sections of the second suction portion of thenominal airfoil profile at each Z coordinate value, the suction sidesections of the second suction portion of the nominal airfoil profileare coupled together to define the second suction portion, the secondsuction portion comprises a second portion length along the Z axis, thesecond portion length is less than or equal to the airfoil length, andthe first and second suction portions are offset from one another alongthe Z axis.
 3. The system of claim 1, wherein the airfoil comprises afirst pressure portion of the nominal airfoil profile substantially inaccordance with the Cartesian coordinate values of X, Y, and Z of apressure side as set forth in TABLE I to the maximum of three decimalplaces, wherein the X and Y values of the pressure side are coordinatevalues that couple together to define pressure side sections of thefirst pressure portion of the nominal airfoil profile at each Zcoordinate value, the pressure side sections of the first pressureportion of the nominal airfoil profile are coupled together to definethe first pressure portion, the first pressure portion comprises asecond portion length along the Z axis, and the second portion length isless than or equal to the airfoil length.
 4. The system of claim 3,wherein the first suction portion and the first pressure portion atleast partially overlap with one another along the Z axis; and whereinthe first and second portion lengths are substantially the same, and thefirst and second portion lengths start at a common distance relative toa base of the airfoil and extend toward a tip of the airfoil.
 5. Thesystem of claim 1, wherein the first portion length of the first suctionportion starts at a distance relative to a base of the airfoil andextends toward a tip of the airfoil; and wherein the first portionlength includes greater than or equal to two consecutive Cartesiancoordinate values of Z in TABLE I.
 6. The system of claim 1, wherein thefirst portion length is equal to or greater than 10 percent of theairfoil length.
 7. The system of claim 1, wherein the first portionlength is equal to or greater than 25 percent of the airfoil length. 8.The system of claim 1, wherein the first portion length is equal to orgreater than 50 percent of the airfoil length.
 9. The system of claim 1,wherein the first portion length is equal to or greater than 75 percentof the airfoil length.
 10. The system of claim 1, wherein the firstportion length is equal to 100 percent of the airfoil length.
 11. Thesystem of claim 1, wherein the airfoil comprises the nominal airfoilprofile substantially in accordance with Cartesian coordinate values ofX, Y, and Z as set forth in TABLE I to the maximum of three decimalplaces along an entirety of both the suction side and a pressure side ofthe airfoil.
 12. The system of claim 1, wherein the airfoil comprises acoating disposed over the first suction portion of the nominal airfoilprofile substantially in accordance with the Cartesian coordinate valuesof X, Y, and Z of the suction side as set forth in TABLE I to themaximum of three decimal places; and wherein the coating increases the Xand Y values of the suction side in TABLE I to the maximum of threedecimal places by no greater than approximately 3.5 mm along the firstsuction portion.
 13. The system of claim 1, comprising a plurality ofcompressor airfoils of a compressor stage, wherein each of the pluralityof compressor airfoils comprises the airfoil having the first suctionportion of the nominal airfoil profile substantially in accordance withthe Cartesian coordinate values of X, Y, and Z of the suction side asset forth in TABLE I to the maximum of three decimal places.
 14. Thesystem of claim 1, comprising a gas turbine engine having a compressor,a combustor, and a turbine; wherein the compressor comprises theairfoil.
 15. The system of claim 1, wherein the airfoil is a first stagecompressor airfoil.
 16. The system of claim 15, wherein the airfoil is acompressor stator vane.
 17. The system of claim 1, wherein the airfoilcomprises the first suction portion of the nominal airfoil profilesubstantially in accordance with Cartesian coordinate values of X, Y,and Z of the suction side as set forth in TABLE I to a maximum of fourdecimal places.
 18. The system of claim 1, wherein the airfoil comprisesthe first suction portion of the nominal airfoil profile substantiallyin accordance with Cartesian coordinate values of X, Y, and Z of thesuction side as set forth in TABLE I to a maximum of five decimalplaces.
 19. A system comprising: an airfoil comprising a suction side ofa nominal airfoil profile substantially in accordance with Cartesiancoordinate values of X, Y, and Z of the suction side as set forth inTABLE I to a maximum of three decimal places, wherein the X and Y valuesof the suction side are coordinate values that couple together to definesuction side sections of the suction side of the nominal airfoil profileat each Z coordinate value, the suction side sections of the suctionside of the nominal airfoil profile are coupled together to define thesuction side, and the Cartesian coordinate values of X, Y, and Z arenon-dimensional values convertible to dimensional distances.
 20. Asystem comprising: an airfoil comprising a nominal airfoil profilesubstantially in accordance with Cartesian coordinate values of X, Y,and Z as set forth in TABLE I to a maximum of three decimal places,wherein the X and Y values are coordinate values that couple together todefine airfoil sections of the nominal airfoil profile at each Zcoordinate value, the airfoil sections of the nominal airfoil profileare coupled together to define an entirety of the airfoil, and theCartesian coordinate values of X, Y, and Z are non-dimensional valuesconvertible to dimensional distances.